US9592916B2 - Aircraft air conditioning system and method for controlling an aircraft air conditioning system using a bypass valve - Google Patents

Aircraft air conditioning system and method for controlling an aircraft air conditioning system using a bypass valve Download PDF

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Publication number
US9592916B2
US9592916B2 US13/847,337 US201313847337A US9592916B2 US 9592916 B2 US9592916 B2 US 9592916B2 US 201313847337 A US201313847337 A US 201313847337A US 9592916 B2 US9592916 B2 US 9592916B2
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air
mixing chamber
volume flow
air conditioning
aircraft
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US20130248164A1 (en
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Jürgen Kelnhofer
Dariusz Krakowski
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Airbus Operations GmbH
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Airbus Operations GmbH
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Assigned to AIRBUS OPERATIONS GMBH reassignment AIRBUS OPERATIONS GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KRAKOWSKI, DARIUSZ, KELNHOFER, JURGEN
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B64D13/08—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned the air being heated or cooled
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B64D2013/0603—Environmental Control Systems
    • B64D2013/0611—Environmental Control Systems combined with auxiliary power units (APU's)
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B64D2013/0603—Environmental Control Systems
    • B64D2013/0655—Environmental Control Systems with zone or personal climate controls
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B64D2013/0603—Environmental Control Systems
    • B64D2013/0688—Environmental Control Systems with means for recirculating cabin air
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/50—On board measures aiming to increase energy efficiency
    • Y02T50/56—

Definitions

  • the present invention relates to a method for controlling an aircraft air conditioning system and to an aircraft air conditioning system.
  • So-called air-based air conditioning systems are usually used at present in commercial aircraft to air-condition the aircraft cabin.
  • An aircraft air conditioning system serves to cool the aircraft cabin, which would otherwise be overheated due to thermal loads, such as, for example, body heat of the passengers and waste heat from equipment present on board the aircraft.
  • the aircraft air conditioning system in addition adequately supplies fresh air into the aircraft cabin to ensure that a prescribed minimum proportion of oxygen is present in the aircraft cabin.
  • Air-based air conditioning systems typically comprise an air conditioning unit, which is arranged, for example, in a wing root of the aircraft, and which is supplied with compressed process air that is generated by a compressor or bled of from an engine or an auxiliary power unit (APU) of the aircraft.
  • air conditioning unit usually is used so as to supply the air conditioning unit of the aircraft air conditioning system with compressed process air.
  • the air conditioning unit of the aircraft air conditioning system typically is supplied with compressed process air from the auxiliary power unit of the aircraft.
  • the process air upon flowing through at least one heat exchanger as well as through various compression and expansion units, is cooled and expanded.
  • Cooled process air exiting the air conditioning unit finally is supplied to a mixing chamber where it is mixed with recirculation recirculated from an aircraft region to be air conditioned.
  • the mixed air from the mixing chamber via respective mixed air lines, is supplied to the aircraft region to be air conditioned which may be divided into a plurality of air conditioning zones.
  • the invention is directed at the object of specifying a method for controlling an aircraft air conditioning system, that allows a source of compressed process air to be supplied to the aircraft air conditioning system, such as for example an auxiliary power unit, to be operated in an energy-efficient manner. Further, the invention is directed at the object of providing an aircraft air condition system, that allows a source of compressed process air to be supplied to the aircraft air conditioning system, such as for example an auxiliary power unit, to be operated in an energy-efficient manner.
  • This object is achieved by a method for controlling an aircraft air conditioning system having features of claims herein and an aircraft air conditioning system having features of claims herein.
  • a heating demand or a cooling demand of an aircraft region to be air conditioned is detected.
  • the aircraft region to be air conditioned may be an aircraft passenger cabin, a cockpit, a freight compartment or any other aircraft region.
  • the heating or cooling demand of the aircraft region to be air conditioned may, for example, be detected on the basis of a comparison of a set temperature in the aircraft region to be air conditioned with an actual temperature in the aircraft region to be air conditioned, wherein the actual temperature in the aircraft region to be air conditioned may, for example, be measured by a suitable temperature sensor.
  • the set temperature in the aircraft region to be air conditioned may, for example, be determined by a user and entered via a suitable user interface of the air conditioning system or may be a temperature value which is stored in a control unit, preferably an electronic control unit for controlling the operation of the aircraft air conditioning system.
  • the control unit for controlling the operation of the aircraft air conditioning system may also be used for determining the heating or cooling demand of the aircraft region to be air conditioned.
  • a volume flow of recirculation air discharged from the aircraft region to be air conditioned and a volume flow of compressed air into a mixing chamber of the aircraft air conditioning system is controlled such that the heating or cooling demand of the aircraft region to be air conditioned is met, while the volume flow of compressed air into the mixing chamber of the aircraft air conditioning system is minimized.
  • the volume flow of recirculation air thus, beside the volume flow of compressed air into the mixing chamber of the aircraft air conditioning system, is used as a direct control parameter for controlling the operation of the aircraft air conditioning system in dependence on the heating or cooling demand of the aircraft region to be air conditioned. This allows the implementation of a control strategy aiming at a minimization of the volume flow of compressed air into the mixing chamber of the aircraft air conditioning system.
  • the compressed air may be provided by a compressed air source, such as for example a compressor, an engine or an auxiliary power unit of the aircraft.
  • the compressed air provided by the compressed air source may be cooled and expanded in an air conditioning unit of the aircraft air conditioning system.
  • the air cooled by the air conditioning unit, for appropriately adjusting the temperature of the air which is finally supplied to the mixing chamber, in an exit region of the air conditioning unit may be mixed with additional compressed hot air supplied from the compressed air source.
  • “Compressed air” in the context of the present application thus may contain compressed air from a compressed air source which is cooled and expanded in an air conditioning unit and/or hot compressed air which is directly bled off the compressed air source.
  • the performance requirements placed on the compressed air source can be reduced.
  • the method for controlling an aircraft air conditioning system allows a particularly energy efficient operation of the compressed air source. Further, in particular if an engine or an auxiliary power unit of the aircraft is used as the compressed air source, fuel consumption and wear of the engine or the auxiliary power unit can be reduced.
  • a volume flow of recirculation air discharged from the aircraft region to be air conditioned into the mixing chamber may be increased.
  • a set temperature of the mixed air in the mixing chamber typically is relatively high and may, for example, be between approximately 15 to approximately 70° C.
  • the volume flow of recirculation air from the aircraft region to be air conditioned into the mixing chamber may be increased, for example, by increasing the speed of recirculation fans conveying the recirculation air from the aircraft region to be air conditioned into the mixing chamber.
  • the volume flow of compressed air into the mixing chamber then is decreased in dependence on the increase of the volume flow of recirculation air into the mixing chamber.
  • the volume flow of recirculation air discharged from the aircraft region to be air conditioned into the mixing chamber is increased and the volume flow of compressed air into the mixing chamber is decreased until it has reached the predetermined minimum value allowing a particularly energy efficient operation of the compressed air source.
  • the decrease of the volume flow of compressed air into the mixing chamber may be adjusted to the increase of the volume flow of recirculation air into the mixing chamber such that a combined volume flow of recirculation air and compressed air is kept constant.
  • the control strategy of increasing the recirculation air volume flow and correspondingly decreasing the compressed air volume flow into the mixing chamber is implemented only if the volume flow of compressed air into the mixing chamber still has not reached the predetermined minimum value.
  • the volume flow of compressed air into the mixing chamber preferably corresponds to the predetermined minimum value, when an air conditioning unit of the aircraft air conditioning system is operated with its maximum cooling capacity, i.e., cools the compressed air to the lowest possible temperature, and a supply of hot compressed air to the air cooled by the air conditioning unit is interrupted.
  • the supply of hot compressed air to the air cooled by the air conditioning unit may be decreased and finally interrupted by closing a bypass valve provided in a bypass line being connected to the compressed air source and opening into a line connecting the air conditioning unit to the mixing chamber downstream of the air conditioning unit.
  • the bypass valve may be a valve having a variable flow cross section. When the bypass valve is fully closed, the supply of hot compressed air to the air cooled by the air conditioning unit is interrupted.
  • the increase of the volume flow of recirculation air into the mixing chamber is stopped, as soon as an actual temperature of the mixed air in the mixing chamber corresponds to a set temperature of the mixed air in the mixing chamber.
  • the set temperature of the mixed air in the mixing chamber may be associated with the heating demand of the aircraft region to be air conditioned.
  • the volume flow of compressed air into the mixing chamber may be increased from the predetermined minimum value, if it is determined that an actual temperature of the mixed air in the mixing chamber is below a set temperature of the mixed air in the mixing chamber, although the volume flow of recirculation air into the mixing chamber has reached a predetermined maximum value.
  • the volume flow of recirculation air into the mixing chamber may correspond to the predetermined maximum value, for example, when recirculation fans conveying the recirculation air from the aircraft region to be air conditioned to the mixing chamber are operated with the maximum speed.
  • the predetermined maximum value of the volume flow of recirculation air into the mixing chamber may be a volume flow value that is determined in dependence on the heating demand of the aircraft region to be air conditioned and the actual temperature of the recirculation air.
  • the volume flow of compressed air into the mixing chamber may be increased from the predetermined minimum value, if the heating demand of the aircraft region to be air conditioned cannot be met by further increasing the volume flow of recirculation air, for example, due to performance restrictions of the recirculation fans or since the actual temperature of the recirculation air is too low.
  • a volume flow of air cooled by the air conditioning unit of the aircraft air conditioning system into the mixing chamber may be decreased.
  • the actual temperature of the mixed air in the mixing chamber increases. Therefore, a volume flow of hot compressed air which is supplied to the air cooled by the air conditioning unit is decreased in dependence on the decrease of the volume flow of air cooled by the air conditioning unit.
  • the increase of the temperature of the mixed air in the mixing chamber caused by the reduction of the volume flow of air cooled by the air conditioning unit can be compensated for.
  • the combined compressed air volume flow formed by the volume flow of air cooled by the air conditioning unit and the volume flow of hot compressed air which is supplied to the air cooled by the air conditioning unit is reduced.
  • the volume flow of air cooled by the air conditioning unit into the mixing chamber and the volume flow of compressed air which is supplied to the air cooled by the air conditioning unit are decreased until the air conditioning unit is operated with its maximum cooling capacity, i.e., cools the compressed air to the lowest possible temperature, and a supply of hot compressed air to the air cooled by the air conditioning unit is minimized and, if possible, interrupted.
  • the volume flow of recirculation air into the mixing chamber may be increased. Due to the increase of the volume flow of relatively warm recirculating air into the mixing chamber, the supply of hot compressed air to the air cooled by the air conditioning unit may be decreased in dependence on the increase of the volume flow of recirculation air into the mixing chamber. As a result, the combined volume flow of compressed air into the mixing chamber can further be reduced.
  • An aircraft air conditioning system comprises means for determining a heating or cooling demand of an aircraft region to be air conditioned and a control unit which is adapted to control a volume flow of recirculation air discharged from the aircraft region to be air conditioned and a volume flow of compressed air into a mixing chamber of the aircraft air conditioning system such that the heating or cooling demand of the aircraft region to be air conditioned is met, while the volume flow of compressed air to the mixing chamber of the aircraft air conditioning system is minimized.
  • control unit may be adapted to increase a volume flow of recirculation air discharged from the aircraft region to be air conditioned into the mixing chamber, and to decrease the volume flow of compressed air into the mixing chamber in dependence of the increase of the volume flow of recirculation air into the mixing chamber.
  • this control strategy is implemented until the volume flow of compressed air into the mixing chamber has reached the predetermined minimum value.
  • the volume flow of compressed air into the mixing chamber corresponds to the predetermined minimum value, when an air conditioning unit of the aircraft air conditioning system is operated with its maximum cooling capacity, and a supply of hot compressed air to the air cooled by the air conditioning unit is interrupted.
  • the control unit may be adapted to stop the increase of the volume flow of recirculation air into the mixing chamber, after the volume flow of compressed air into the mixing chamber has reached the predetermined minimum value, as soon as an actual temperature of the mixed air in the mixing chamber corresponds to a set temperature of the mixed air in the mixing chamber, the set temperature of the mixed air in the mixing chamber being associated with the heating demand of the aircraft region to be air conditioned.
  • the control unit may further be adapted to increase the volume flow of compressed air into the mixing chamber from the predetermined minimum value, if it is determined that an actual temperature of the mixed air in the mixing chamber is below a set temperature of the mixed air in the mixing chamber, although the volume flow of recirculation air into the mixing chamber has reached a predetermined maximum value.
  • control unit may be adapted to decrease a volume flow of air cooled by the air conditioning unit of the aircraft air conditioning system into the mixing chamber, and to decrease a volume flow of hot compressed air which is supplied to the air cooled by the air conditioning unit.
  • this control strategy is implemented until the air conditioning unit of the aircraft air conditioning system is operated with its maximum cooling capacity.
  • the control unit may be adapted to decrease the volume flow of hot compressed air which is supplied to the air cooled by the air conditioning unit by closing a bypass valve provided in a bypass line being connected to a compressed air source and opening into a line connecting the air conditioning unit to the mixing chamber downstream of the air conditioning unit.
  • the control unit may be adapted to increase the volume flow of recirculation air into the mixing chamber if it is determined that hot compressed air is supplied to the air cooled by the air conditioning unit, although the air conditioning unit of the aircraft air conditioning system is operated with its maximum cooling capacity.
  • the control unit may further be adapted to decrease the volume flow of hot compressed air which is supplied to the air cooled by the air conditioning unit in dependence on the increase of the volume flow of recirculation air into the mixing chamber.
  • FIG. 1 shows an aircraft air conditioning system which is supplied with compressed fresh air by means of an auxiliary power unit
  • FIG. 2 shows a detail of the aircraft air conditioning system according to FIG. 1 ,
  • FIG. 3 shows an air distribution system of the aircraft air conditioning system according to FIG. 1 ,
  • FIG. 4 shows a diagram depicting the control of the aircraft air conditioning system according to FIG. 1 .
  • FIG. 5 shows a flow diagram of a method for operating the aircraft air conditioning system according to FIG. 1 in a heating mode
  • FIG. 6 shows a flow diagram of a method for operating the aircraft air conditioning system according to FIG. 1 in a cooling mode.
  • FIG. 1 shows an aircraft air conditioning system 10 , which, during ground operation of the aircraft, is supplied with compressed process air from an auxiliary power unit 1 .
  • the compressed air generated by the auxiliary power unit 12 is supplied to the aircraft air conditioning system 10 , specifically an air conditioning unit 14 of the air conditioning 10 via a line 16 .
  • a valve 18 is disposed in the line 16 which controls the supply of compressed process air into the air conditioning unit 14 of the aircraft air conditioning system 10 .
  • the process air upon flowing through at least one heat exchanger and upon flowing through various compression and expansion units, is cooled and expanded.
  • a bypass line 22 branches off from the line 16 upstream of the air conditioning unit 14 and opens into the line 20 downstream of the air conditioning unit 14 .
  • a bypass valve 24 is disposed in the bypass line 22 .
  • Hot process air bled off the auxiliary power unit 12 , via the bypass line 22 may bypass the air conditioning unit 14 and may be mixed with the cool air exiting the air conditioning unit 14 downstream of the air conditioning unit 14 .
  • the bypass valve 14 the temperature of the process air at the exit of the air conditioning unit 14 may be controlled as desired.
  • compressed air which may be a mixture of air cooled and expanded by the air conditioning unit 14 and hot compressed air which is supplied to the air cooled in the air conditioning unit 14 via the bypass line 22 , is guided into a mixing chamber 26 .
  • the compressed air is mixed with recirculation air discharged from an aircraft region 28 to be air conditioned by means of recirculation fans 30 .
  • Mixed air from the mixing chamber 26 finally is supplied to the aircraft region 28 to be air conditioned via an air distribution system 32 .
  • the operation of the aircraft air conditioning system 10 is controlled by means of an electronic control unit 34 .
  • An electronic control unit 36 serves to control the operation of the auxiliary power unit 12 .
  • a first signal line 38 connects the control unit 36 for controlling the auxiliary power unit 12 to the auxiliary power unit 12 .
  • a second signal line 40 connects the electronic control unit 34 for controlling the air conditioning system 10 to the air conditioning unit 14 .
  • the electronic control unit 34 is connected to the recirculation fans 30 and adapted to control the operation of the recirculation fans 30 .
  • the electronic control unit 34 is connected to the bypass valve 24 and adapted to control the operation of the bypass valve 24 .
  • the control units 34 , 36 communicate with each other via a third signal line 42 .
  • a temperature sensor 44 is disposed in the aircraft region 28 to be air conditioned, which, via a fourth signal line 46 , provides signals indicative of the actual temperature in the aircraft region 28 to be air conditioned to an electronic control unit 48 .
  • the electronic control unit 48 via a fifth signal line 50 , is connected to an input device 52 .
  • the electronic control unit 48 determines a heating or cooling demand of the aircraft region 28 to be air conditioned. For determining the heating or cooling demand of the aircraft region 28 to be air conditioned, the electronic control unit 48 may, for example, compare an actual temperature in the aircraft region 28 to be air conditioned with a set temperature in the aircraft region 28 to be air conditioned.
  • the actual temperature in the aircraft region 28 to be air conditioned may be measured by means of the temperature sensor 44 which is disposed in the aircraft region 28 to be air conditioned.
  • the set temperature in the aircraft region 28 to be air conditioned may, for example, be input by a user via the input device 52 or may be stored in a storage device of the electronic control unit 48 .
  • a further temperature sensor 54 is disposed in the mixing chamber 26 of the air conditioning system 10 .
  • a sixth signal line 46 connects the temperature sensor to an electronic control unit 58 . Based the heating or cooling demand of the aircraft region 28 to be air conditioned, which is communicated to the electronic control unit 58 via a seventh signal line 60 , the electronic control unit 58 determines a set temperature of the mixed air in the mixing chamber 26 . Further, the electronic control unit 58 compares the set temperature of the mixed air in the mixing chamber 26 with the actual temperature of the mixed air in the mixing chamber 26 which is measured by means of the temperature sensor 54 .
  • the electronic control unit 48 and the electronic control 58 both, via an eighth signal line 62 , communicate with the electronic control unit 34 of the air conditioning system 10 .
  • the electronic control unit 34 controls the operation of the air conditioning unit 14 and thus the temperature and the volume flow of cool air exiting the air conditioning unit 14 .
  • the electronic control unit 34 controls the bypass valve 24 and thus the supply of hot compressed air to the cool air exiting the air conditioning unit 14 .
  • the electronic control unit 34 controls the operation of the recirculation fans 30 and thus the volume flow of recirculation air conveyed by the recirculation fans 30 from the aircraft region 28 to be air conditioned into the mixing chamber 26 .
  • the electronic control unit 34 via the third signal line 42 , communicates with the electronic control unit 36 of the auxiliary power unit 12 which controls the operation of the auxiliary power unit 12 in dependence on the data provided by the electronic control unit 34 of the air conditioning system 10 .
  • control tasks to different electronic control units is merely an example of how the air conditioning system 10 and the auxiliary power unit 12 may be controlled. It is, of course, also conceivable to use a smaller number of control units or only one control unit for implementing the control strategies which will be described in more detail in the following. Further, instead of signal lines, wireless data transmission may be employed.
  • the electronic control unit 34 of the air conditioning system 10 controls the volume flow of recirculation air discharged from the aircraft region 28 to be air conditioned and the volume flow of compressed air, i.e., a combined volume flow of cool air exiting the air conditioning unit 14 and hot compressed air supplied to the cool air exiting the air conditioning unit 14 via the bypass line 22 , into the mixing chamber 26 such that the heating or cooling demand of the aircraft region 28 to be air conditioned is met, while the volume flow of compressed air into the mixing chamber 26 is minimized. Minimizing the volume flow of compressed air into the mixing chamber 26 allows a particularly energy efficient operation of the auxiliary power unit 12 . Specifically, fuel consumption and wear of the auxiliary power unit 12 can be reduced.
  • FIG. 5 shows a flow diagram of a method for operating the aircraft air conditioning system 10 in a heating mode, i.e., in a case wherein the electronic control unit 48 , for the aircraft region 28 to be air conditioned, has determined a heating demand.
  • the electronic control unit 34 analyses, whether the volume flow of compressed air into the mixing chamber 26 of the air conditioning system 10 exceeds a predetermined minimum value.
  • the volume flow of compressed air into the mixing chamber 26 corresponds to the predetermined minimum value, when the air conditioning unit 14 is operated with its maximum cooling capacity, i.e., cools the compressed air to the lowest possible temperature, and the supply of hot compressed air to the air cooled by the air conditioning unit 14 is interrupted, i.e., the bypass valve 24 disposed in the bypass line 22 is closed. If the volume flow of compressed air into the mixing chamber 26 corresponds to the predetermined minimum value, the control strategy simply is maintained, i.e., no changes in the volume flows of compressed air and recirculation air into the mixing chamber 26 are initiated.
  • the volume flow of compressed air into the mixing chamber 26 exceeds the predetermined minimum value, the volume flow of recirculation air discharged from the aircraft region 28 to be air conditioned into the mixing chamber 26 is increased by increasing the speed of the recirculation fans 30 .
  • the volume flow of typically relatively warm recirculation air into the mixing chamber 26 the actual temperature of the mixed air in the mixing chamber 26 is increased so as to approach the set temperature.
  • the volume flow of compressed air into the mixing chamber 26 is decreased in dependence on the increase of the volume flow of recirculation air into the mixing chamber 26 .
  • the decrease of the volume flow of compressed air into the mixing chamber 26 is adjusted to the increase of the volume flow of recirculation air into the mixing chamber 26 such that a combined volume flow of recirculation air and compressed air is kept constant.
  • the increase of the volume flow of recirculation air into the mixing chamber 26 is stopped, as soon as an actual temperature of the mixed air in the mixing chamber 26 corresponds to the set temperature of the mixed air in the mixing chamber 26 which is determined by the control unit 58 based on the heating demand of the aircraft region 28 to be air conditioned.
  • the entire control procedure it is possible to increase the volume flow of compressed air into the mixing chamber 26 from the predetermined minimum value or any other value, if it is determined that the actual temperature of the mixed air in the mixing chamber 26 is below the set temperature of the mixed air in the mixing chamber 26 , although the volume flow of recirculation air into the mixing chamber 26 has reached a predetermined maximum value, i.e., the recirculation fans 30 are operated with the maximum speed.
  • the predetermined maximum value of the volume flow of recirculation air into the mixing chamber is determined in dependence on the heating demand of the aircraft region 28 to be air conditioned and the actual temperature of the recirculation air which typically corresponds to the actual temperature in the aircraft region 28 to be air conditioned and which may be measured by means of the temperature sensor 44 .
  • the volume flow of compressed air into the mixing chamber 26 is increased, if the heating demand of the aircraft region 28 to be air conditioned cannot be met by further increasing the volume flow of recirculation air, for example, due to performance restrictions of the recirculation fans 30 or since the actual temperature of the recirculation air is too low.
  • FIG. 6 shows a flow diagram of a method for operating the air conditioning system 10 in a cooling mode, i.e., a method for operating the aircraft air conditioning system 10 in case a cooling demand of the aircraft region 28 to be air conditioned is determined by the electronic control unit 48 .
  • the control unit 34 in a first step, again analyses whether the volume flow of compressed air into the mixing chamber 26 exceeds the predetermined minimum value or not.
  • the control strategy is not changed, i.e., the volume flows of compressed air and recirculation air into the mixing chamber 26 are kept constant.
  • the electronic control unit 34 determines, that the volume flow of compressed air into the mixing chamber 26 exceeds the predetermined minimum value, the volume flow of air cooled by the air conditioning unit 14 of the aircraft air conditioning system 10 into the mixing chamber 26 is decreased. As a result, the actual temperature of the mixed air in the mixing chamber 26 increases. Therefore, the volume flow of hot compressed air which is supplied to the air cooled by the air conditioning unit 14 is decreased in dependence on the decrease of the volume flow of air cooled by the air conditioning unit 14 by closing the bypass valve 24 . As a result, the increase of the temperature of the mixed air in the mixing chamber 26 caused by the reduction of the volume flow of air cooled by the air conditioning unit 14 is compensated for.
  • the volume flow of air cooled by the air conditioning unit 14 into the mixing chamber 26 and the volume flow of compressed air which is supplied to the air cooled by the air conditioning unit 14 are decreased until the air conditioning unit 14 is operated with its maximum cooling capacity, i.e., cools the compressed air to the lowest possible temperature, and the supply of hot compressed air to the air cooled by the air conditioning unit 14 is minimized and, if possible, interrupted by closing the bypass valve 24 .
  • the control unit 34 determines whether hot compressed air is supplied to the air cooled by the air conditioning unit 14 . If it is determined by the control unit 34 that hot compressed air is supplied to the air cooled by the air conditioning unit 14 , although the air conditioning unit 14 is operated with its maximum cooling capacity, the volume flow of recirculation air into the mixing chamber 26 is increased. Due to the increase of the volume flow of relatively warm recirculating air into the mixing chamber 26 , it is possible to decrease the supply of hot compressed air to the air cooled by the air conditioning unit 14 in dependence on the increase of the volume flow of recirculation air into the mixing chamber 26 . As a result, the combined volume flow of compressed air into the mixing chamber 26 can further be reduced.
  • the increase of the volume flow of recirculation air into the mixing chamber 26 is stopped, as soon as an actual temperature of the mixed air in the mixing chamber 26 corresponds to the set temperature of the mixed air in the mixing chamber 26 which is determined by the control unit 58 based on the heating demand of the aircraft region 28 to be air conditioned.
US13/847,337 2012-03-21 2013-03-19 Aircraft air conditioning system and method for controlling an aircraft air conditioning system using a bypass valve Active 2034-06-25 US9592916B2 (en)

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Application Number Priority Date Filing Date Title
US13/847,337 US9592916B2 (en) 2012-03-21 2013-03-19 Aircraft air conditioning system and method for controlling an aircraft air conditioning system using a bypass valve

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
US201261613506P 2012-03-21 2012-03-21
EP12002004.5A EP2664544B1 (en) 2012-03-21 2012-03-21 Method for controlling an aircraft air conditioning system and aircraft air conditioning system
EP12002004 2012-03-21
EP12002004.5 2012-03-21
US13/847,337 US9592916B2 (en) 2012-03-21 2013-03-19 Aircraft air conditioning system and method for controlling an aircraft air conditioning system using a bypass valve

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